Airplane construction



Feb. 16, 1932. U L 1,845,648

AIRPLANE CONSTRUCTION Filed Feb. 4, 1929 s Sheets-Sheet 1 avwwto'c i Feb. 16, 1932.

v. J. B URNELLI AIRPLANE CONSTRUCTION Filed Feb. 4. 1929 3 Sheets-Sheet 2 FeB I6, '1 932.

V. J. BURNELLI AIRPLANE CONSTRUCTION Filed Feb. 4, 1929 3 Sheets-Sheet 3 L awmmtoz m gmame/It ill Patented Feb. 16, 1932 UNITED STATES PATENT OFFICE VINCENT I. BUBNELLI, 0! NEW YORK, IT. Y, ABSIGNOB 1'0 THE UPIEBOU-BUBNELIII OOBPORATION, 1 COBPOBATIOH' OI DELAWARE nmmr. OONSTBUOTION Application med February 4, 1929. Serial Io. 887,198.. i

This invention relates to the frame construction oi" airplane fuselages, and my improvement is directed particularly to the simple and economical manufacture and as sembly oi the elements comprised in a Inetcllic ironic structure wherein the use oi gusscts d and uncle longdrons areemplofycd out rent W to provide the required area for river, diagonal. members 1 Another feature of my invention consists of the tuseluge construction adapted to pro vide the requisite strength therein in view of its miusua-illy large size, and the novel character oil the trussmg em loyed to suit certain structural conditions, all as will be explained in detail in the accom anying descri tion.

Uther leatures an advantages 0 my in vention hereinafter appear.

lo the drawin gsz Figure l is a side elevation of an airplane fuselage, "Without the covering.

2 an enlarged detail, in perspective, showing a portion of a longron, and a bulkhead and diagonal members attached therec.

Fig, aglan view of Fig. 1.

Fig, 4t a etail view of a bulkhead on line M of llligr F ti is a detail view of the front spar bulk ead, and h B is a detail view of the rear spar bulkea In said figures let '1 indicate the upper longrons, and 2 the lower longrons' of an airfoil fuselage, the airplane indicated being.

of the TElurnelli type.

These longrons, see the detail view, Fig. Q, are metallic angle bars, having the wide flanges h, at, the extended width thereof serving to provide sufiicient riveting area for the attachment thereto of bulkheads and diagonals, "winch heretofore required the interposi tion oi guess-ts in the joint regions. Thus the bulkhead element 5, of T-shape in cross-section, is shown as havin its flanges riveted respectively to the 1011 ron 3, 4, the width of the latter afiording ample area for the application of a sufiicient number of u hereto the bulkheads and rivets to assure the creation of a secure union between the connected elements.

For bulkhead reinforcement, a plate 6 is laced across the angle of the an ular memers of the bulkhead element, stud plate be ing riveted to the Web of said element,

Also the diagonal elements l, of T-shupe in cross-section, are scoured by rivetin ntheir flanges to the Wide flanges 3, fl; of the ongdron without the intervention of gussetsu In Fig. 3 I have shown a fuselage struc-- ture of unusual size. This view 18 a to plan, showing the upper longrons l. at one side of the fuselage, and also an intermediate lengthwise stifiening member 8 (see Fig, coextensive therewlth, a similar intermediate stifi'ening member 8a extending intermediate the lower longrons, 2, illlengthwise at c the fuselage bottom,

These stlflening members 8, 8a are rendered necessary by reason of the relativel large area encompassed in the fuselage w ich requires that the longrons be supplemented with intermediate reinforcement, both for lengthwise compression purposes and as of for '11 additional anchorages and for a d ouble stem of trusslng which ave found desirab e to employ in theproduction of so large a fuselage.

Between the fronuspar bulkhead 9 and rear-spar b 10, where the greatest strength is required, crossed truss members 11, 11a are provided at each side of the memher 8 respectively tying said member to the ion rons 1 at opposite sides of the fuselage. Similar'crossed truss members (not shown) are provided between bulkheads 9, 10 at each side of member 80, respectively tying said member to the longrons 2 at opposite sides of the fuselage.

ltearward of the rear spar bulkhead 10am the succeeding bulkheads 13, 14, 15 and 16, trussing 17, 18, similar to that provided tween bulkheads 9, 10 being disposed reepeo tively between bulkheads 10 and 14 and between bulkheads 14 and 16, excepting that elements of trussing 17 are angled respectively from the ofgosite sides of bulkhead 13 to the centres o ulkheads 10, 1d; and the elehientsof trussing 18 are angled respective- 1% from the o posite sides of bulkhead'15 to t e centres of ulkheads 14,16.

Also, truss elements 19 extend res ectively from the centre of bulkhead 16 to t e opposite sides of the frame 20 which constitutes the fuselage end.

\ head, includes the horizontal frame elements .21, 21a, respectivelytoward the upper and lower ends of the bulkhead, and the vertical frame elements 22, 23, 24, 25, 26, in spaced relation across the width of the bulkhead.

This bulkhead 9 separates the pilots compartment or cockpit 27 from the passenger or load compartment 28; and windows 29, 29, located respectively in the partition spaces formed between the vertical elements 22,23; 22, 24, above horizontal element 21, enable the pilots to view the interior of the passengers compartments and to see for themselves that the doors are closed and all is in readiness for taking off. V

Also between the elements 23, and 24, 26, respectively, doorways 30, 30 are provided as means of communication between the com artments. t T e end panels 31, 31 of the frame are reinforced by inclined braces 32, 32 respectively. 1

Bulkhead 10, which includes the vertical frame element 10a, is provided interiorly with a web 33 that has a central, depending extension 33a which connects with a rectangular structure 34, providing couches at opposite sides of said extension. The web 33 and its extension 33a, which are reinforced by flanges 33b, form'boundaries for' clearances 35, 36 that render the passenger compartment continuous throughsaid bulkhead. The contour of the web 33 is such asto provide head room while adding great strength to the bulkhead.

Between the bulkheads" 9 and 10 (also between bulkheads 10 and 13) a system of trussing is provided at the respective sides of the fuselage that. strengthens the frame while enabling ample window space to be provided for observation use of passengers seated the fuselage.

Thus, for example, longitudinal compression members 37 extend between bulkheads 9 and 10 toward their upper portions. These members 37 are intersected centrally by vertical members 38. Inclined trusses 39 extend from the bottom of members 38 to the respective ends of members 37, and inclined trusses 40 extend from the top of members 38 to the respective ends of members 37. The windowframes 41 are mounted between the ong the walls of of my members 37, 38 39, to thereby provide window spaces whose area is relatively unobed in their under surfaces, these clearances being intended to afford recesses for the reception of the wheels 43 of a retractible chassis 44 when said wheels have been swung up against the bottom of the fuselage into horizontal positions."

This application is acontinuation in art application Serial No. 435,481, ed January 6, 1921. I

Variations within the spirit and scopeof my invention are equally comprehended by the foregoing disclosure.

Iclaim: 1. The combination in an airplane fuselage of unusual width hav'ig a frame including upper and lower lon rons, of upper and lower longitudinal sti emng members located intermediate the longrons and trust ing disposed respectively between the longrons and stiffening members.

2. The combination in an airplane fuselage of a front spar bulkhead provided with aced horizontal members and s aced vertical members, window openings ing provided between adjacent vertical members above the upper horizontal member an doorways being provided between ad acent vertical members and said-horizontal members at opposite sides of said bulkhead.

3. The combination in an airplane fuselage of a rear spar bulkhead having a frame and a central vertical member, a web extended inwardly from said frame and opposingly from said central member, said web having reinforce flanges at its edge and being contoured to provide suitable clearances.

4. The combination in an a' lane fuselage having a number of b eads, in spaced relation, of longitudinal compression members between adjacent bulkheads, toward the upper portion thereof, vertical members intermediate said adjacent bulkheads, diagonal trussmembers extending from the bottom of said vertical members to the respective outerends of said compression members, and window frames enclosed respectively between rs and compression member's.

5. The combination in an airplane fuselage, havin a, foldable chassis carrying wheels, of a .ont spar bulkhead whose frame portion at its bottom is rovided with recesses adapted for the reception of said wheels.

Executed this30th day of J anu VINCENT J. B

said vertical members, diagonal truss memurposes, for the be 

